US10730633B2 - Hybrid electric aircraft propulsion system with motors using induction effect - Google Patents
Hybrid electric aircraft propulsion system with motors using induction effect Download PDFInfo
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- US10730633B2 US10730633B2 US15/358,595 US201615358595A US10730633B2 US 10730633 B2 US10730633 B2 US 10730633B2 US 201615358595 A US201615358595 A US 201615358595A US 10730633 B2 US10730633 B2 US 10730633B2
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- 230000006698 induction Effects 0.000 title claims abstract description 15
- 230000000694 effects Effects 0.000 title claims abstract description 11
- 230000005284 excitation Effects 0.000 claims abstract description 19
- 230000001360 synchronised effect Effects 0.000 claims description 19
- 238000000034 method Methods 0.000 claims description 9
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 230000004044 response Effects 0.000 claims description 3
- 230000006870 function Effects 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000001143 conditioned effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000003292 diminished effect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000011022 operating instruction Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 239000013598 vector Substances 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
-
- B64D2027/026—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y02T50/64—
Definitions
- This invention generally relates to electric motors propelled aircraft, and more particularly, this invention relates to a method and system to control motors with induction effect used to provide hybrid electric propulsion for an aircraft.
- Hybrid electric propulsion offers increased maneuverability for aerospace applications and is currently one of the top choices for vertical take-off and vertical landing aircraft. At the same time hybrid electric propulsion increases safety and reliability over traditional systems. It also offers easier maintenance, together with environmental and cost benefits.
- hybrid electric propulsion systems consist of an engine, that can be a turbine engine, driving a generator to produce electric power which is distributed and conditioned to supply electric motors that drive the propulsion fans or propellers of the aircraft.
- a hybrid electric aircraft propulsion system includes a motor or plurality of motors to drive a propeller or propulsion fan.
- the motors are directly supplied from the electrical output of a generator.
- the generator is driven by a variable speed engine and as such the generator has a rotating speed proportional to the speed of the engine.
- a controller is operatively coupled to the motor, the generator and the engine. The controller is operable to control a speed of the engine and a excitation of the generator to provide an output at a target voltage and frequency to drive the motor at a desired torque and speed.
- An aircraft is provided with a hybrid electric propulsion system.
- the hybrid electric aircraft propulsion system includes a motor to drive a propeller or propulsion fan.
- the motors are directly supplied from the electrical output of a generator.
- the generator is driven by a variable speed engine and as such the generator has a rotating speed proportional to the speed of the engine.
- a controller is operatively coupled to the motor, the generator and the engine. The controller is operable to control a speed of the engine and a excitation of the generator to provide an output at a target voltage and frequency to drive the motor at a desired torque and speed.
- a hybrid electric aircraft propulsion system that includes a motor to drive a propeller or propulsion fan, and where the motors are directly supplied from the electrical output of a generator
- the generator is driven by a variable speed engine and as such the generator has a rotating speed proportional to the speed of the engine.
- the motor torque and rotational speed is controlled by controlling a speed of the engine and a excitation of the generator to provide an output at a target voltage and frequency to drive the motor.
- FIG. 1 is a functional block diagram of a hybrid electric propulsion system in accordance with various herein described exemplary embodiments
- FIG. 2 is a functional block diagram of an alternative exemplary embodiment of a hybrid electric propulsion system
- FIG. 3 graphic depiction of aircraft that may incorporate a hybrid electric propulsion system in accordance with one or more of the herein described exemplary embodiments.
- system or module may refer to any combination or collection of mechanical and electrical hardware, software, firmware, electronic control component, processing logic, and/or processor device, individually or in any combination, including without limitation: application specific integrated circuit (ASIC), an electronic circuit, a processor (shared, dedicated, or group), memory that executes one or more software or firmware programs, a combinational logic circuit, and/or other suitable components that provide the described functionality.
- ASIC application specific integrated circuit
- processor shared, dedicated, or group
- memory executes one or more software or firmware programs, a combinational logic circuit, and/or other suitable components that provide the described functionality.
- Embodiments of the invention may be described herein in terms of functional and/or logical block components and various processing steps. It should be appreciated that such block components may be realized by any number, combination or collection of mechanical and electrical hardware, software, and/or firmware components configured to perform the specified functions. For example, an embodiment of the invention may employ various combinations of electrical components, e.g., sensors, integrated circuit components, memory elements, digital signal processing elements, logic elements, look-up tables, or the like, which may carry out a variety of functions under the control of one or more microprocessors or other control devices.
- electrical components e.g., sensors, integrated circuit components, memory elements, digital signal processing elements, logic elements, look-up tables, or the like, which may carry out a variety of functions under the control of one or more microprocessors or other control devices.
- embodiments of the present invention may be practiced in conjunction with any number of mechanical and/or electronic systems, and that the systems described herein are merely exemplary embodiment of the invention.
- FIG. 1 provides a schematic depiction of a hybrid electric propulsion system 10 that includes a turbine engine 12 operatively coupled to drive a generator 14 an electrical power output 16 of which is coupled to a motor 18 that drives one or more propulsion structures 20 , e.g., propellers or propulsion fans of an aircraft 22 (see FIG. 3 ).
- a turbine engine 12 operatively coupled to drive a generator 14 an electrical power output 16 of which is coupled to a motor 18 that drives one or more propulsion structures 20 , e.g., propellers or propulsion fans of an aircraft 22 (see FIG. 3 ).
- propulsion structures 20 e.g., propellers or propulsion fans of an aircraft 22 (see FIG. 3 ).
- the motor 18 is driven directly by the electrical power output 16 of the generator 14 .
- the speed and torque output of the motor 18 is controlled to a given rotational speed based upon the propulsion characteristics of the propulsion structures 20 to meet a thrust requirement of the aircraft 22 for a given operating condition. For example, maximum thrust may be required for take off, climb out and landing, while less thrust may be required for normal cruise flight.
- V voltage
- f g frequency of the electrical output 16 of the generator 14
- Generator output 16 control is accomplished by controlling the rotating speed of the turbine engine 12 and an excitation of the field (not depicted) of the generator 14 .
- a controller 24 is operatively coupled to each of the turbine engine 12 , the generator 14 and the motor 18 and to a control input 26 .
- the control input 26 may be provided from an operator control, an automated flight control or any other suitable arrangement operable to provide to the controller 24 the control signal 26 which may be data representing a desired/required thrust, a target rotational speed of the motor 18 or other suitable operating indication, and by the direct or geared coupling of the motor 18 with corresponding propulsion structure 20 , a corresponding rotational speed of the propulsion structure 20 .
- the controller further receives periodic indications of the actual rotational speed of the motor 18 .
- the controller 24 delivers operating data 28 , such as a motor speed signal, to the turbine engine 12 , and in particularly to an engine controller (not depicted) associated with the turbine engine 12 .
- the engine controller controls the supply of fuel and combustion air and other operating characteristics such that the turbine engine 12 achieves a target operating rotational speed.
- the output of the turbine engine 12 is coupled directly or through a gear box (not depicted) to the generator 14 , driving the generator 14 and the result that the generator 14 rotating speed is the same as or proportional to the rotating speed of the turbine engine 12 .
- the controller 24 further delivers an excitation control signal 30 to the generator 14 , and in particular, to a generator control (not depicted).
- the generator control adjusts a field excitation of the generator 14 such that the field windings (not depicted) of the generator 14 are excited to create a desired flux.
- the generator 14 Responsive to being rotationally driven by the turbine engine 12 and given the field excitation, the generator 14 provides the generator output 16 to the motor 18 at the desired voltage (V) and frequency (f g ). In response thereto, the motor 18 drives the propulsion structure 20 at a desired rotating speed to achieve a required operating thrust.
- the thrust can be also be varied by controlling the pitch of the propeller or by changing the nozzle area of the propulsion fans.
- the motor 18 being a motor with induction effect has the capability to operate directly from the alternating current (AC) power output 16 of the generator 14 .
- This motor can be an induction motor (IM), a wound-field synchronous motor (WFSM) with damper bars (as are known and not depicted) providing sufficient induction effect or permanent magnet (PM) motor with induction effect.
- IM induction motor
- WFSM wound-field synchronous motor
- PM permanent magnet
- the motor 18 also has the capability to start directly from the power output 16 , but this comes at the expense of potentially large in-rush currents during start.
- the system 10 may control the voltage and the frequency supplied to the motor 18 at start so as to reduce the inrush current, which is another desirable feature of this system.
- the system 10 is operable to receive the control input 26 indicative of a desired thrust output of the propulsion system 20 .
- the controller 24 additionally receives motor 18 operating data 32 which may include present rotating speed.
- the controller 24 which may include a processor coupled to a memory containing operating instructions (not depicted) to affect the herein described functionality, is operable based at least upon the control input 26 and operating data 28 to determine a require voltage (V) and frequency (f g ) input to the motor 18 to achieve the motor 18 rotating speed in order to achieve the desired thrust from the propulsion system 20 .
- the voltage (V) and the frequency (f g ) correlates to a generator 14 rotating speed and field excitation.
- the controller accordingly provides a speed signal 28 to the turbine engine 12 controller, and a excitation output 30 to the generator 14 .
- the turbine engine 12 controller adjusts operating parameters of the turbine engine 12 , and for example among various control parameters, an amount of fuel and combustion air provided thereto, to drive the generator 14 at a first rotational speed. Additionally, responsive to the field signal 30 , the generator 14 controller energizes the generator field to provide a first field energization so that for a first rotational speed, the generator 14 provides the generator output 16 at the required voltage (V) and frequency (f g ).
- the controller 24 may periodically receive control input 26 and operating data 28 , and responsive thereto, adjust the speed signal 28 and excitation signal 30 to operate the turbine engine 12 at a second rotational speed and to energize the field at a second field energization.
- the excitation to this motor is turned on only after it has started using the induction effect provided by its damper bars and when it is running close to synchronous speed. By turning on its excitation, this motor will run synchronously with the generator's output and it will have high efficiency and power factor providing an optimum system.
- FIG. 1 illustrates a single motor 18 /propulsion system 20 combination.
- FIG. 2 illustrates a propulsion system 38 .
- the propulsion system 38 includes a turbine engine 12 coupled to a generator 14 that provides generator output 16 .
- the system 38 include a plurality of motors 18 , each of which is coupled to a propulsion system 20 .
- the generator output 16 may be directly coupled to each of the motors 18 , or as depicted in FIG. 2 , the generator output 16 may be coupled to a bus 40 and from the bus 40 via switches 42 the generator output 16 may coupled to the motors 18 .
- the switches 42 may be any suitable mechanical actuating or high-speed, high power electronic switches such as insulated gate bi-polar transistor (IGBT) type high-power electronic switches.
- IGBT insulated gate bi-polar transistor
- the generator output 16 is provided to each motor 18 , and hence, the thrust output of each of the propulsion systems 20 will be relatively equal.
- the switches 42 provide a level of individual control of the motor 18 /propulsion system 20 arrangements. As is known, the switches 42 may be used to turn on or off of the output power 16 respectively to each motor 18 . As such, the output of the corresponding propulsion system 20 is affected, essentially diminished in view of the interruption of the generator output power 16 being delivered to a number of motors 18 to provide thrust control for propulsion system 20 .
- the controller 24 may provide switch control signals 44 to the switches 42 responsive to the control signal 26 and the operating data 28 .
- FIG. 3 illustrates an aircraft 22 that may be provided with a hybrid electric propulsion system such as, for example, a system 10 or a system 38 .
- the aircraft 22 is depicted with a pivoting nacelle 46 . While a single nacelle 46 is shown, the aircraft in a typical configuration would have nacelles 46 on each of the port and starboard wings.
- the nacelle 46 may pivot such that thrust from a propeller or fan structure 20 may be directed substantially horizontally, substantially vertically and at various vectors therebetween.
- This aircraft configuration to include pivoting nacelles allows for very short take-off and landing (VSTOL) operating capability.
- VSTOL take-off and landing
- hybrid propulsion systems in accordance with the herein described embodiments may be adapted to virtually any aircraft including fixed wing, rotorcraft (helicopter), tilt-rotor ( FIG. 3 ) and the like. This includes distributed propulsion using multiple fans along the aircraft structure or embedded in the airframe.
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- Aviation & Aerospace Engineering (AREA)
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Abstract
Description
Claims (15)
Priority Applications (1)
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US15/358,595 US10730633B2 (en) | 2016-11-22 | 2016-11-22 | Hybrid electric aircraft propulsion system with motors using induction effect |
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US15/358,595 US10730633B2 (en) | 2016-11-22 | 2016-11-22 | Hybrid electric aircraft propulsion system with motors using induction effect |
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US20180141671A1 US20180141671A1 (en) | 2018-05-24 |
US10730633B2 true US10730633B2 (en) | 2020-08-04 |
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Cited By (5)
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US11196585B1 (en) | 2021-03-31 | 2021-12-07 | Beta Air, Llc | Method and system for virtualizing a plurality of controller area network bus units communicatively connected to an aircraft |
US11447015B1 (en) | 2021-06-15 | 2022-09-20 | Beta Air, Llc | System and method for dynamic excitation of an energy storage element configured for use in an electric aircraft |
US11682535B2 (en) | 2021-03-12 | 2023-06-20 | Essex Industries, Inc. | Rocker switch |
US11688568B2 (en) | 2021-03-15 | 2023-06-27 | Essex Industries, Inc. | Five-position switch |
US20240017823A1 (en) * | 2022-07-18 | 2024-01-18 | Textron Innovations Inc. | Optimizing usage of supplemental engine power |
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US10934008B2 (en) * | 2017-02-10 | 2021-03-02 | General Electric Company | Dual function aircraft |
US10807729B2 (en) * | 2017-05-17 | 2020-10-20 | General Electric Company | Propulsion system for an aircraft |
US10974826B2 (en) * | 2017-05-22 | 2021-04-13 | Overair, Inc. | EVTOL having many variable speed tilt rotors |
KR102483971B1 (en) | 2017-05-22 | 2023-01-02 | 오버에어, 인코퍼레이티드 | Evtol aircraft using large, variable speed tilt rotors |
CN109383783B (en) * | 2018-08-31 | 2022-07-26 | 辽宁同心圆科技有限公司 | Energy-saving power-assisting system of aero-engine |
CN109204797B (en) * | 2018-08-31 | 2022-07-26 | 辽宁同心圆科技有限公司 | Energy-saving power assisting device of aero-engine |
CN109383784B (en) * | 2018-08-31 | 2022-06-14 | 辽宁同心圆科技有限公司 | Aerial platform with power assisting system |
US11814187B2 (en) | 2020-12-21 | 2023-11-14 | General Electric Company | Hybrid electric propulsor equipped with a hydraulic coupling |
DE102022205488A1 (en) * | 2022-05-31 | 2023-11-30 | Rolls-Royce Deutschland Ltd & Co Kg | Sizing the gap between substrate and heat sink in high-voltage power converters |
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Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11682535B2 (en) | 2021-03-12 | 2023-06-20 | Essex Industries, Inc. | Rocker switch |
US11688568B2 (en) | 2021-03-15 | 2023-06-27 | Essex Industries, Inc. | Five-position switch |
US11196585B1 (en) | 2021-03-31 | 2021-12-07 | Beta Air, Llc | Method and system for virtualizing a plurality of controller area network bus units communicatively connected to an aircraft |
US11447015B1 (en) | 2021-06-15 | 2022-09-20 | Beta Air, Llc | System and method for dynamic excitation of an energy storage element configured for use in an electric aircraft |
US20240017823A1 (en) * | 2022-07-18 | 2024-01-18 | Textron Innovations Inc. | Optimizing usage of supplemental engine power |
Also Published As
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US20180141671A1 (en) | 2018-05-24 |
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